function [cd_0_body]=body_drag(geo_loc, flight_cond_loc, S_wing)
	%Function to compute zero lift drag for thefuselage at a given flight condition
	% Examples:
	% To FUSELAGE Cd_0 at CRUISE call cd_0_fus_cruise=body_drag(geo.fus, flight_cond.cruise)		

	Rey=flight_cond_loc.tas*flight_cond_loc.rho*geo_loc.lenght/flight_cond_loc.mu; % Fuselage lenght Reynolds number
	
	% Wing-fuselage interference factor
	R_wt=1; %See pg 151, fig 5.12, Roskan performance book
	% Insert here a dialog box showing the fuselage lengh Reynolds number and Mach number and the figure 5.12. Ask for the R_wt factor!
	
	% Turbulent flat plate friction coeficient
	C_f_surf=0.455/(log10(Rey)^2.58*(1+0.144*flight_cond_loc.Mach^2)*0.58); %Turbulent mean skin friction coeficient
	
	cd_0_body=R_wt*C_f_surf*(1+60/((geo_loc.lenght/geo_loc.eq_dia)^3)+0.0025*(geo_loc.lenght/geo_loc.eq_dia))*geo_loc.s_wet/S_wing;













